jsbsim.js
Version:
JSBSim flight dynamics model ported to JavaScript
896 lines (874 loc) • 37.3 kB
text/xml
<fdm_config name="c182" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Unknown </author>
<filecreationdate> 2002-01-01 </filecreationdate>
<version> $Id: c182.xml,v 1.24 2012/12/22 15:22:21 jberndt Exp $ </version>
<description> Cessna C-182 </description>
<note>
This model was created using publicly available data, publicly available
technical reports, textbooks, and guesses. It contains no proprietary or
restricted data. If this model has been validated at all, it would be
only to the extent that it seems to "fly right", and that it possibly
complies with published, publicly known, performance data (maximum speed,
endurance, etc.). Thus, this model is meant for educational and entertainment
purposes only.
This simulation model is not endorsed by the manufacturer. This model is not
to be sold.
</note>
</fileheader>
<metrics>
<wingarea unit="FT2"> 174 </wingarea>
<wingspan unit="FT"> 35.8 </wingspan>
<chord unit="FT"> 4.9 </chord>
<htailarea unit="FT2"> 21.9 </htailarea>
<htailarm unit="FT"> 15.7 </htailarm>
<vtailarea unit="FT2"> 16.5 </vtailarea>
<vtailarm unit="FT"> 0 </vtailarm>
<location name="AERORP" unit="IN">
<x> 43.2 </x>
<y> 0 </y>
<z> 59.4 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 37 </x>
<y> 0 </y>
<z> 48 </z>
</location>
<location name="VRP" unit="IN">
<x> 43.9 </x>
<y> 0 </y>
<z> 40.6 </z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 948 </ixx>
<iyy unit="SLUG*FT2"> 1346 </iyy>
<izz unit="SLUG*FT2"> 1967 </izz>
<emptywt unit="LBS"> 1700 </emptywt>
<location name="CG" unit="IN">
<x> 41 </x>
<y> 0 </y>
<z> 36.5 </z>
</location>
<pointmass name="name">
<weight unit="LBS"> 180 </weight>
<location name="POINTMASS" unit="IN">
<x> 36 </x>
<y> -14 </y>
<z> 24 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="IN">
<x> -6.8 </x>
<y> 0 </y>
<z> -20 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 1800 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 600 </damping_coeff>
<max_steer unit="DEG"> 10 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN">
<location unit="IN">
<x> 58.2 </x>
<y> -43 </y>
<z> -17.9 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
<max_steer unit="DEG"> 360.0 </max_steer>
<brake_group> LEFT </brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MAIN">
<location unit="IN">
<x> 58.2 </x>
<y> 43 </y>
<z> -17.9 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
<max_steer unit="DEG"> 360.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="TAIL_SKID">
<location unit="IN">
<x> 188 </x>
<y> 0 </y>
<z> 8 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<rolling_friction> 0.2 </rolling_friction>
<spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="LEFT_TIP">
<location unit="IN">
<x> 43.2 </x>
<y> -214.8 </y>
<z> 59.4 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<rolling_friction> 0.2 </rolling_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_TIP">
<location unit="IN">
<x> 43.2 </x>
<y> 214.8 </y>
<z> 59.4 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<rolling_friction> 0.2 </rolling_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
</ground_reactions>
<propulsion>
<engine file="engIO540AB1A5">
<location unit="IN">
<x> -19.7 </x>
<y> 0 </y>
<z> 26.6 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<feed>1</feed>
<thruster file="prop_81in2v">
<location unit="IN">
<x> -37.7 </x>
<y> 0 </y>
<z> 26.6 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
<sense> 1 </sense>
<p_factor> 10 </p_factor>
</thruster>
</engine>
<tank type="FUEL"> <!-- Tank number 0 -->
<location unit="IN">
<x> 56 </x>
<y> -112 </y>
<z> 59.4 </z>
</location>
<capacity unit="LBS"> 300 </capacity>
<contents unit="LBS"> 200 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 1 -->
<location unit="IN">
<x> 56 </x>
<y> 112 </y>
<z> 59.4 </z>
</location>
<capacity unit="LBS"> 300 </capacity>
<contents unit="LBS"> 200 </contents>
</tank>
</propulsion>
<flight_control name="FCS: c182">
<channel name="Pitch">
<summer name="Pitch Trim Sum">
<input>fcs/elevator-cmd-norm</input>
<input>fcs/pitch-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
</summer>
<aerosurface_scale name="Elevator Control">
<input>fcs/pitch-trim-sum</input>
<gain>0.01745</gain>
<range>
<min>-28</min>
<max>23</max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Elevator position normalized">
<input>fcs/elevator-pos-deg</input>
<domain>
<min>-25</min>
<max>35</max>
</domain>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/elevator-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Roll">
<summer name="Roll Trim Sum">
<input>fcs/aileron-cmd-norm</input>
<input>fcs/roll-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
</summer>
<aerosurface_scale name="Aileron Control">
<input>fcs/roll-trim-sum</input>
<gain>0.01745</gain>
<range>
<min>-20</min>
<max>15</max>
</range>
<output>fcs/left-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Left Aileron position normalized">
<input>fcs/left-aileron-pos-deg</input>
<domain>
<min>-20</min>
<max>15</max>
</domain>
<range>
<min>-0.75</min>
<max>1</max>
</range>
<output>fcs/left-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron position normalized">
<input>fcs/right-aileron-pos-deg</input>
<domain>
<min>-20</min>
<max>15</max>
</domain>
<range>
<min>-0.75</min>
<max>1</max>
</range>
<output>fcs/right-aileron-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Yaw">
<summer name="Yaw Trim Sum">
<input>fcs/rudder-cmd-norm</input>
<input>fcs/yaw-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
</summer>
<aerosurface_scale name="Rudder Control">
<input>fcs/yaw-trim-sum</input>
<gain>0.01745</gain>
<range>
<min>-16</min>
<max>16</max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Rudder position normalized">
<input>fcs/rudder-pos-deg</input>
<domain>
<min>-25</min>
<max>25</max>
</domain>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/rudder-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Flaps">
<kinematic name="Flaps Control">
<input>fcs/flap-cmd-norm</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>10</position>
<time>2</time>
</setting>
<setting>
<position>20</position>
<time>1</time>
</setting>
<setting>
<position>30</position>
<time>1</time>
</setting>
</traverse>
<output>fcs/flap-pos-deg</output>
</kinematic>
<aerosurface_scale name="Flap position normalized">
<input>fcs/flap-pos-deg</input>
<domain>
<min>0</min>
<max>30</max>
</domain>
<range>
<min>0</min>
<max>1</max>
</range>
<output>fcs/flap-pos-norm</output>
</aerosurface_scale>
</channel>
</flight_control>
<aerodynamics>
<function name="aero/function/kCLge">
<description>Change_in_lift_due_to_ground_effect</description>
<product>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 1.2030
0.1000 1.1270
0.1500 1.0900
0.2000 1.0730
0.3000 1.0460
0.4000 1.0550
0.5000 1.0190
0.6000 1.0130
0.7000 1.0080
0.8000 1.0060
0.9000 1.0030
1.0000 1.0020
1.1000 1.0000
</tableData>
</table>
</product>
</function>
<axis name="DRAG">
<function name="aero/coefficient/CDo">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value>0.027</value>
</product>
</function>
<function name="aero/coefficient/CDalpha">
<description>Drag_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-0.0873 0.0041
-0.0698 0.0013
-0.0524 0.0001
-0.0349 0.0003
-0.0175 0.0020
0.0000 0.0052
0.0175 0.0099
0.0349 0.0162
0.0524 0.0240
0.0698 0.0334
0.0873 0.0442
0.1047 0.0566
0.1222 0.0706
0.1396 0.0860
0.1571 0.0962
0.1745 0.1069
0.1920 0.1180
0.2094 0.1298
0.2269 0.1424
0.2443 0.1565
0.2618 0.1727
0.2793 0.1782
0.2967 0.1716
0.3142 0.1618
0.3316 0.1475
0.3491 0.1097
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDbeta">
<description>Drag_due_to_sideslip</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/mag-beta-rad</property>
<value>0.1700</value>
</product>
</function>
<function name="aero/coefficient/CDDf">
<description>Drag_due_to_flap_deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 10.0000 20.0000 30.0000
-0.0873 0.0000 0.0030 0.0084 0.0153
-0.0698 0.0000 0.0061 0.0131 0.0208
-0.0524 0.0000 0.0092 0.0178 0.0263
-0.0349 0.0000 0.0124 0.0225 0.0317
-0.0175 0.0000 0.0155 0.0272 0.0372
0.0000 0.0000 0.0186 0.0319 0.0427
0.0175 0.0000 0.0218 0.0367 0.0483
0.0349 0.0000 0.0250 0.0415 0.0539
0.0524 0.0000 0.0282 0.0463 0.0594
0.0698 0.0000 0.0314 0.0511 0.0650
0.0873 0.0000 0.0346 0.0558 0.0706
0.1047 0.0000 0.0378 0.0606 0.0762
0.1222 0.0000 0.0409 0.0654 0.0818
0.1396 0.0000 0.0441 0.0702 0.0873
0.1571 0.0000 0.0461 0.0731 0.0907
0.1745 0.0000 0.0480 0.0760 0.0941
0.1920 0.0000 0.0499 0.0789 0.0975
0.2094 0.0000 0.0518 0.0818 0.1008
0.2269 0.0000 0.0538 0.0847 0.1043
0.2443 0.0000 0.0559 0.0879 0.1080
0.2618 0.0000 0.0582 0.0913 0.1120
0.2793 0.0000 0.0590 0.0925 0.1133
0.2967 0.0000 0.0581 0.0911 0.1117
0.3142 0.0000 0.0567 0.0890 0.1093
0.3316 0.0000 0.0546 0.0859 0.1056
0.3491 0.0000 0.0485 0.0767 0.0950
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDDe">
<description>Drag_due_to_Elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/mag-elevator-pos-rad</property>
<value>0.0000</value>
</product>
</function>
</axis>
<axis name="SIDE">
<function name="aero/coefficient/CYb">
<description>Side_force_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/beta-rad</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.3930
0.0943 -0.4040
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CYp">
<description>Side_force_due_to_roll_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.0750
0.0943 -0.1450
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CYr">
<description>Side_force_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 0.2140
0.0943 0.2670
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CYDa">
<description>Side_force_due_to_aileron</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/left-aileron-pos-rad</property>
<value>0.0000</value>
</product>
</function>
<function name="aero/coefficient/CYDr">
<description>Side_force_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rudder-pos-rad</property>
<value>0.1870</value>
</product>
</function>
</axis>
<axis name="LIFT">
<function name="aero/coefficient/CLo">
<description>Lift_at_zero_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<value>0.3070</value>
</product>
</function>
<function name="aero/coefficient/CLalpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-0.0900 -0.5270
0.0000 -0.0570
0.1400 0.7130
0.2100 0.9450
0.2400 1.0470
0.2600 1.1330
0.2800 1.1590
0.3000 1.1250
0.3200 1.0740
0.3400 0.9910
0.3600 0.6630
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLDf">
<description>Lift_due_to_flap_deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<table>
<independentVar>fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 0.0000
10.0000 0.2000
20.0000 0.3000
30.0000 0.3500
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLadot">
<description>Lift_due_to_alpha_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/alphadot-rad_sec</property>
<property>aero/ci2vel</property>
<value>1.7000</value>
</product>
</function>
<function name="aero/coefficient/CLq">
<description>Lift_due_to_pitch_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>velocities/q-aero-rad_sec</property>
<property>aero/ci2vel</property>
<value>3.9000</value>
</product>
</function>
<function name="aero/coefficient/CLDe">
<description>Lift_due_to_elevator_deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-rad</property>
<value>0.4300</value>
</product>
</function>
</axis>
<axis name="ROLL">
<function name="aero/coefficient/Clb">
<description>Roll_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<table>
<independentVar lookup="row">aero/beta-rad</independentVar>
<independentVar lookup="column">aero/alpha-rad</independentVar>
<tableData>
0.0000 0.0943
-0.3490 0.0322 0.0312
0.0000 0.0000 0.0000
0.3490 -0.0322 -0.0312
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Clp">
<description>Roll_moment_due_to_roll_rate_(roll_damping)</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.4840
0.0943 -0.4870
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Clr">
<description>Roll_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 0.0798
0.0943 0.1869
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/ClDa">
<description>Roll_moment_due_to_aileron</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<value>0.15</value>
</product>
</function>
<function name="aero/coefficient/ClDr">
<description>Roll_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value>-0.0147</value>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/coefficient/Cmo">
<description>Pitching_moment_at_zero_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<value>0.0400</value>
</product>
</function>
<function name="aero/coefficient/Cmalpha">
<description>Pitch_moment_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/alpha-rad</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.6130
0.0943 -0.6500
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmadot">
<description>Pitch_moment_due_to_alpha_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>aero/alphadot-rad_sec</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -7.2700
0.0943 -5.5700
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmq">
<description>Pitch_moment_due_to_pitch_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>velocities/q-aero-rad_sec</property>
<value>-12.4000</value>
</product>
</function>
<function name="aero/coefficient/CmDf">
<description>Pitch_moment_due_to_flap_deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table>
<independentVar>fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 0.0000
10.0000 -0.0654
20.0000 -0.0981
30.0000 -0.1140
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CmDe">
<description>Pitch_moment_due_to_elevator_deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elevator-pos-rad</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.6220
0.0943 -0.8690
</tableData>
</table>
</product>
</function>
</axis>
<axis name="YAW">
<function name="aero/coefficient/Cnb">
<description>Yaw_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 0.0587
0.0943 0.0907
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnp">
<description>Yaw_moment_due_to_roll_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.0278
0.0943 -0.0649
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnr">
<description>Yaw_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.0937
0.0943 -0.1199
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CnDa">
<description>Yaw_moment_due_to_aileron</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.0216
0.0943 -0.0504
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CnDr">
<description>Yaw_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.0645
0.0943 -0.0805
</tableData>
</table>
</product>
</function>
</axis>
</aerodynamics>
</fdm_config>